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Effect of variation of chord and span of ailerons on hinge moments at several angles of pitch
This report presents the results of an investigation of the hinge moments of ailerons of various chords and spans on two airfoils having the Clark Y and USA-27 wing sections, supplementing the investigations described in NACA-TR-298 and NACA-TR-343, of the rolling and yawing moments due to similar ailerons on these two airfoil sections. The measurements were made at various angles of pitch, but at zero angle of roll and yaw, the wing chord being set at an angle of +4 degrees to the fuselage axis.
Date:
August 11, 1930
Creator:
Monish, B. H.
System:
The UNT Digital Library